6x5 (6x5.dat) v2025-1001 Simulation Date: 02/24/2026 ----- AIRFOIL SUMMARY DATA ----- DEFINITIONS: THE QUOTED PITCH REFLECTS, IN GENERAL, ANGULAR MEASURE AS DEFINED WITH A FLAT BOTTOM SURFACE. THIS WILL AGREE WITH A PRATHER GAGE MEASUREMENT OVER MOST OF THE EFFECTIVE PORTION OF THE BLADE. (NOTE: QUOTED=INPUT) THE LE-TE MEASURE IS DEFINED IN TERMS OF LEADING EDGE AND TRAILING EDGE (MOLD) PARTING LINE DATUMS. THE PRATHER MEASURE REFLECTS THE MOST LIKELY PITCH INTERPRETATION FROM A PITCH MEASUREMENT DEVICE THAT RESTS AGAINST THE LOWER SURFACE. SWEEP & RAKE ARE DEFINED WITH (MOLD) LE PARTING LINE. ZHIGH IS HIGHEST ELEVATION ON TOP SURFACE. TWIST IS DEFINED WITH (MOLD) LE AND TE PARTING LINE DATUMS. CHORD IS THE LENGTH BETWEEN (MOLD) LE AND TE PARTING LINES. CGY IS MASS OFFSET, FORE-AFT. CGZ IS MASS OFFSET, ELEVATION. STATION CHORD PITCH PITCH PITCH SWEEP(Y) RAKE(Z) THICKNESS TWIST MAX-THICK CROSS-SECTION ZHIGH CGY CGZ (IN) (IN) (QUOTED) (LE-TE) (PRATHER) (IN) (IN) RATIO (DEG) (IN) (IN**2) (IN) (IN) (IN) 0.0000 0.6500 0.9416 0.0000 0.0000 0.3250 0.0000 0.3846 0.0000 0.2500 0.0000 0.0600 0.0000 0.0000 0.0725 0.6123 1.3565 0.0080 -0.2713 0.3076 0.0045 0.3833 1.0077 0.2347 0.1304 0.0643 -0.0012 -0.0571 0.1450 0.5740 1.7491 0.0634 -0.5268 0.2919 0.0166 0.3795 3.9815 0.2179 0.1268 0.0759 0.0029 -0.0525 0.2175 0.5392 2.1193 0.2112 -0.6834 0.2778 0.0346 0.3732 8.7865 0.2012 0.1203 0.0931 0.0082 -0.0434 0.2900 0.5124 2.4671 0.4924 -0.6586 0.2656 0.0564 0.3643 15.1225 0.1867 0.1118 0.1138 0.0144 -0.0309 0.3625 0.4971 2.7925 0.9375 -0.3824 0.2553 0.0805 0.3529 22.3723 0.1754 0.1021 0.1363 0.0209 -0.0165 0.4350 0.4942 3.0956 1.5547 0.1864 0.2469 0.1049 0.3389 29.6322 0.1675 0.0922 0.1586 0.0270 -0.0015 0.5075 0.5016 3.3763 2.3131 1.0334 0.2407 0.1280 0.3224 35.9566 0.1617 0.0827 0.1788 0.0322 0.0130 0.5800 0.5147 3.6347 3.1260 2.0576 0.2366 0.1478 0.3033 40.6223 0.1561 0.0740 0.1952 0.0357 0.0258 0.6525 0.5282 3.8706 3.8478 3.0573 0.2347 0.1626 0.2817 43.1837 0.1488 0.0663 0.2060 0.0372 0.0361 0.7250 0.5379 4.0842 4.2978 3.7548 0.2351 0.1707 0.2580 43.3338 0.1388 0.0595 0.2095 0.0362 0.0431 0.7974 0.5435 4.2753 4.4998 4.1179 0.2368 0.1733 0.2362 41.9273 0.1284 0.0535 0.2076 0.0340 0.0472 0.8683 0.5478 4.4406 4.6708 4.3937 0.2379 0.1740 0.2176 40.5686 0.1192 0.0487 0.2046 0.0319 0.0494 0.9391 0.5510 4.5844 4.8182 4.5835 0.2384 0.1730 0.2018 39.2357 0.1112 0.0451 0.2006 0.0298 0.0500 1.0098 0.5530 4.7068 4.9434 4.7069 0.2385 0.1703 0.1888 37.9224 0.1044 0.0424 0.1955 0.0276 0.0492 1.0806 0.5540 4.8080 5.0473 4.8081 0.2380 0.1665 0.1785 36.6264 0.0989 0.0402 0.1900 0.0251 0.0481 1.1514 0.5539 4.8878 5.1310 4.8881 0.2371 0.1618 0.1709 35.3463 0.0947 0.0384 0.1842 0.0224 0.0467 1.2222 0.5527 4.9463 5.1954 4.9467 0.2357 0.1562 0.1661 34.0809 0.0918 0.0372 0.1781 0.0194 0.0452 1.2929 0.5505 4.9835 5.2406 4.9839 0.2338 0.1498 0.1636 32.8261 0.0901 0.0363 0.1718 0.0162 0.0434 1.3637 0.5474 4.9994 5.2643 4.9997 0.2314 0.1431 0.1612 31.5658 0.0883 0.0353 0.1653 0.0130 0.0417 1.4345 0.5432 5.0000 5.2723 5.0003 0.2286 0.1362 0.1589 30.3259 0.0863 0.0343 0.1585 0.0099 0.0398 1.5053 0.5381 5.0000 5.2795 5.0003 0.2253 0.1291 0.1566 29.1707 0.0842 0.0331 0.1514 0.0070 0.0376 1.5760 0.5320 5.0000 5.2864 5.0003 0.2216 0.1219 0.1542 28.0951 0.0820 0.0319 0.1441 0.0043 0.0350 1.6468 0.5249 5.0000 5.2930 5.0002 0.2174 0.1145 0.1519 27.0916 0.0797 0.0306 0.1365 0.0017 0.0321 1.7176 0.5168 5.0000 5.2994 5.0002 0.2128 0.1069 0.1496 26.1536 0.0773 0.0292 0.1287 -0.0007 0.0288 1.7884 0.5078 5.0000 5.3055 5.0002 0.2078 0.0991 0.1472 25.2750 0.0748 0.0277 0.1206 -0.0029 0.0252 1.8591 0.4977 5.0000 5.3113 5.0002 0.2024 0.0911 0.1449 24.4507 0.0721 0.0262 0.1122 -0.0051 0.0213 1.9299 0.4867 5.0000 5.3168 5.0001 0.1965 0.0830 0.1425 23.6758 0.0694 0.0247 0.1036 -0.0071 0.0171 2.0007 0.4747 5.0000 5.3220 5.0001 0.1903 0.0747 0.1402 22.9462 0.0666 0.0231 0.0947 -0.0090 0.0126 2.0715 0.4618 5.0000 5.3268 5.0001 0.1837 0.0661 0.1379 22.2579 0.0637 0.0215 0.0856 -0.0108 0.0077 2.1422 0.4478 5.0000 5.3313 5.0001 0.1767 0.0574 0.1355 21.6077 0.0607 0.0199 0.0762 -0.0124 0.0025 2.2130 0.4329 5.0000 5.3354 5.0001 0.1693 0.0485 0.1332 20.9923 0.0577 0.0182 0.0665 -0.0140 -0.0030 2.2838 0.4171 5.0000 5.3391 5.0001 0.1616 0.0393 0.1308 20.4092 0.0546 0.0166 0.0565 -0.0154 -0.0087 2.3546 0.4002 5.0000 5.3425 5.0000 0.1535 0.0300 0.1285 19.8556 0.0514 0.0150 0.0463 -0.0167 -0.0148 2.4253 0.3824 5.0000 5.3454 5.0000 0.1451 0.0204 0.1262 19.3294 0.0482 0.0135 0.0359 -0.0179 -0.0212 2.4961 0.3636 5.0000 5.3478 5.0000 0.1363 0.0106 0.1238 18.8285 0.0450 0.0120 0.0252 -0.0189 -0.0279 2.5669 0.3438 5.0000 5.3498 5.0000 0.1272 0.0006 0.1215 18.3510 0.0418 0.0105 0.0142 -0.0198 -0.0348 2.6377 0.3231 5.0000 5.3514 5.0000 0.1178 -0.0097 0.1192 17.8951 0.0385 0.0091 0.0029 -0.0206 -0.0421 2.7084 0.3013 5.0000 5.3523 5.0000 0.1080 -0.0202 0.1168 17.4592 0.0352 0.0078 -0.0086 -0.0213 -0.0497 2.7792 0.2786 4.9874 5.3401 4.9874 0.0980 -0.0309 0.1145 17.0038 0.0319 0.0065 -0.0204 -0.0218 -0.0575 2.8471 0.2559 4.9213 5.2733 4.9213 0.0880 -0.0415 0.1122 16.4246 0.0287 0.0054 -0.0319 -0.0222 -0.0650 2.8652 0.2483 4.8941 5.2463 4.8945 0.0839 -0.0448 0.1116 16.2473 0.0277 0.0050 -0.0355 -0.0231 -0.0673 2.8803 0.2399 4.8682 5.2208 4.8693 0.0786 -0.0481 0.1111 16.0918 0.0267 0.0047 -0.0391 -0.0248 -0.0696 2.8955 0.2297 4.8395 5.1927 4.8416 0.0716 -0.0518 0.1106 15.9301 0.0254 0.0043 -0.0432 -0.0275 -0.0722 2.9106 0.2173 4.8080 5.1619 4.8134 0.0625 -0.0562 0.1101 15.7621 0.0239 0.0038 -0.0480 -0.0314 -0.0752 2.9258 0.2022 4.7736 5.1284 4.7836 0.0508 -0.0612 0.1096 15.5877 0.0222 0.0033 -0.0536 -0.0366 -0.0787 2.9409 0.1836 4.7365 5.0921 4.7533 0.0357 -0.0671 0.1091 15.4068 0.0200 0.0027 -0.0602 -0.0438 -0.0828 2.9561 0.1596 4.6964 5.0531 4.7242 0.0154 -0.0743 0.1086 15.2195 0.0173 0.0020 -0.0683 -0.0538 -0.0878 2.9712 0.1245 4.6536 5.0116 4.7046 -0.0155 -0.0843 0.1081 15.0268 0.0135 0.0012 -0.0796 -0.0697 -0.0946 2.9864 0.0654 4.6079 4.9696 4.7553 -0.0698 -0.1002 0.1076 14.8340 0.0070 0.0003 -0.0977 -0.0985 -0.1056 3.0000 0.0100 4.5644 4.5644 4.5644 -0.1207 -0.1147 0.1072 13.6122 0.0011 0.0000 -0.1147 0.0000 0.0000 RADIUS: 3.00 PROPELLER RADIUS (IN) HUBRAD: 0.32 HUB RADIUS (IN) HUBTRA: 0.73 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.016074 TOTAL WEIGHT (Kg) = 0.007290 TOTAL VOLUME (IN**3) = 0.261866 TOTAL PROJECTED AREA (IN**2) = 2.4906 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000051 MOMENT OF INERTIA (Kg-M**2) = 0.000006 STATIC MOMENT, ONE SIDE (IN-LB) = 0.006797 SANITY CHECK DATA ARE BELOW DENSITY (SPECIFIC GRAVITY, INPUT FILE) = 1.700 DENSITY (INPUT FILE, LB/IN**3) = 0.6138E-01 AVERAGE DENSITY (FROM WT & VOL ABOVE, LB/IN**3) = 0.6138E-01 ACTIVITY FACTOR = 95.211 INNER LIMIT (NORMALIZED BY RADIUS) = 0.108 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 39562.39 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.00, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 3.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.